多段迭代制导对零窗口发射的适应性研究  

Research on Consecutive Iterative Guidance for Narrow Launch Window

作　　者：吕建强[1] 王晋麟[1] 徐帆[1] Lyu Jian-qiang;Wang Jin-lin;Xu Fan(Beijing Aerospace Automatic Control Institute,Beijing 100854)

机构地区：[1]北京航天自动控制研究所,北京100854

出　　处：《导弹与航天运载技术》2020年第6期46-49,共4页Missiles and Space Vehicles

摘　　要：运载火箭应用迭代制导日益广泛,针对多级火箭零窗口的发射要求,采用多段接力的迭代制导,同时修正迭代制导的目标轨道参数和调整停泊轨道的滑行时间的方法,实现了比单段迭代制导更强的零窗口发射适应能力。通过数学仿真验证了方法的有效性。Iterative guidance has been widely used in the last stage of launch vehicle.According to narrow launch window,consecutive iterative guidance can be used for multiple stages rocket.The method of adjusting target orbit is able to adapt to launching delay in limited condition,while combining the above method and change the period of non-thrust can satisfy narrow launch window better.The numerical simulations implemented demonstrate the effectiveness of the idea.

关 键 词：多段迭代 零窗口发射 停泊轨道 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]